PZL-105 Flaming

PZL-105 Flaming
	PZL-105 at the Polish Aviation Museum
Role	Utility aircraft
Manufacturer	PZL Warszawa-Okęcie
First flight	9 November 1989
Status	Prototype
Primary user	Polish civilian aviation
Number built	2 (prototypes)

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The PZL-105 Flaming (flamingo) is a Polish short-takeoff-and-landing (STOL) utility aircraft designed by PZL "Warszawa-Okęcie". It remained a prototype.

Development

The PZL-105 was designed as a successor to the successful utility aircraft PZL-104 Wilga, being more modern and economical and offering increased transport capacity. The design was initially called Wilga 88. It retained the high-wing layout of the PZL-104 and the upward-opening side doors, but it was a completely new aircraft. Compared with the Wilga, it has a six-seat cabin instead of four seats and the wings are supported by single struts instead of a cantilever design. The plane was intended for a variety of purposes, like glider towing, parachute training, transport, air ambulance, patrolling and crop dusting (with 500 kg of chemicals). Also, a seaplane variant was intended.

The first prototype, powered by a 265 kW (360 hp) Russian M-14P radial engine, was first flown on 9 November 1989 (markings SP-PRC). An intended designation of a serial variant was PZL-105M. The second prototype, designated PZL-105L, was fitted with a flat engine 298 kW (400 hp) Lycoming IO-720. It was flown on 27 July 1991 (markings SP-PRD). There was also made one prototype for static trials.

Problems with funding at the outbreak of the 1980s and 1990s, connected with a change of political system in Poland, and the priority of the PZL-130 Orlik trainer program, had caused the Flaming program to be suspended, and production of the type has yet to have started. The company developed a new variant of the PZL-104, the Wilga 2000 with Lycoming I0-540 flat engine instead.

Design

Metal construction braced high-wing monoplane, conventional in layout, duralumin covered. Semi-monocoque fuselage. Rectangular single-spar wings, fitted with Fowler flaps and slotted flaperons. Six-seat cabin with three rows of seats, with large side doors opening upwards. Conventional fixed landing gear with tail wheel, the main gear is made of composite spring legs. Two-blade or three-blade (PZL-105L) metal propeller. Fuel tanks in wings (270 L).

Surviving aircraft

The first prototype and the second prototype airframe (lacking engine) are in a collection of the Polish Aviation Museum in Kraków.

Specifications (PZL-105M)

Data from Jane's All The World's Aircraft 1993-94.^[1]

General characteristics

Crew: 1
Capacity: 5 pax / 450 kg (990 lb) cargo
Length: 8.7 m (28 ft 7 in)

PZL-105L 8.67 m (28.4 ft)

Wingspan: 12.97 m (42 ft 7 in)
Height: 2.87 m (9 ft 5 in)
Wing area: 16.9 m² (182 sq ft)
Aspect ratio: 9.95
Airfoil: NASA GA(W)-1
Empty weight: 1,130 kg (2,491 lb)

PZL-105L 1,150 kg (2,540 lb)

Max takeoff weight: 1,850 kg (4,079 lb)
Fuel capacity: 270 L (71 US gal; 59 imp gal) in two integral wing tanks
Powerplant: 1 × Vedeneyev M-14P 9-cylinder air-cooled radial piston engine, 268.5 kW (360.1 hp)

PZL-105L 298 kW (400 hp) Lycoming IO-720-A1B

Propellers: 2-bladed W-530TA-D35, 2.4 m (7 ft 10 in) diameter constant-speed propeller

PZL-105L 3-bladed 2.18 m (7 ft 2 in) diameter Hartzell constant-speed propeller

Performance

Maximum speed: 245 km/h (152 mph, 132 kn)

PZL-105L 260 km/h (160 mph; 140 kn)

Cruise speed: 205 km/h (127 mph, 111 kn) max

188 km/h (117 mph; 102 kn) economical

PZL-105L 235 km/h (146 mph; 127 kn) max

PZL-105L 216 km/h (134 mph; 117 kn) economical

Stall speed: 102 km/h (63 mph, 55 kn) flaps down engine idling
Never exceed speed: 306 km/h (190 mph, 165 kn)
Range: 1,044 km (649 mi, 564 nmi) at max cruising speed

1,085 km (674 mi; 586 nmi) at economical cruise speed

PZL-105L 853 km (530 mi; 461 nmi) at max cruising speed

PZL-105L 981 km (610 mi; 530 nmi) at economical cruise speed

Service ceiling: 4,140 m (13,580 ft)

PZL-105L 5,070 m (16,630 ft)

g limits: +3.8 -1.52
Rate of climb: 5.5 m/s (1,080 ft/min) at sea level

PZL-105L 5.6 m/s (1,100 ft/min)

Wing loading: 109.5 kg/m² (22.4 lb/sq ft)
Power/mass: 0.145 kW/kg (0.088 hp/lb)

PZL-105L 0.161 kW/kg (0.098 hp/lb)

Take-off: 176 m (577 ft)
Landing: 153 m (502 ft)
Take-off to 50 m (160 ft): 338 m (1,109 ft)
Landing from 50 m (160 ft): 326 m (1,070 ft)

PZL-105L

Take-off: 189 m (620 ft)
Landing: 157 m (515 ft)
Take-off to 50 m (160 ft): 351 m (1,152 ft)
Landing from 50 m (160 ft): 330 m (1,080 ft)

References

^ Lambert, Mark; Munson, Kenneth; Taylor, Michael J.H., eds. (1993). Jane's all the world's aircraft, 1993-94 (84th ed.). London: Jane's Information Group. pp. 241–242. ISBN 0710610661.

External links

Photos at Lotnictwo.net

[JAWA93-94-1] Lambert, Mark; Munson, Kenneth; Taylor, Michael J.H., eds. (1993). Jane's all the world's aircraft, 1993-94 (84th ed.). London: Jane's Information Group. pp. 241–242. ISBN 0710610661.

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